Abstract: A self-switching dual voltage battery system includes a plurality of battery cell groups connected in series to provide a first voltage between a negative terminal and a first positive terminal. A switch matrix couples a selected one of the plurality of battery cell groups to a second positive terminal to provide a second voltage. A controller coupled to each of the plurality of battery cell groups monitors a charge level associated with each of the plurality of battery cell groups. When the controller determines that the charge level associated with the selected battery cell group falls below a threshold, the controller causes the switch matrix to select another battery cell group from the plurality of battery cell groups to provide the second voltage.

Abstract: Aspects of the present disclosure are presented for a combustion engine design with an optimized amount of materials used to generate the necessary components of the engine. The engine may be generated as a single piece, having no joints, fasteners, or any other areas that could present a risk for damage. The designs are described may also reduce weight of the engine, due to eliminating the need for fasteners and other extraneous hardware. In general, the weight of the engine may be optimized to also preclude the inclusion of extraneous material around needed structures. Also, the engine may be designed to be highly energy efficient, with optimal flows for fuel and other fluid with minimal head loss while maintaining higher pressures.

Abstract: A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to measure the pressure field. The system further includes, but is not limited to, a controller that is communicatively coupled with the plurality of pressure sensors. The controller is configured to receive information that is indicative of the pressure field from the plurality of pressure sensors. The controller is also configured to determine when the pressure field deviates from a desired pressure field based on the information. The controller is also configured to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.

Abstract: A system for facilitating instrument cross-checks between aircrew members using wearable displays includes, but is not limited to, first and second wearable displays configured to be worn by a first and second aircrew members, respectively, and first and second sensors configured to detect first and second orientations of the wearable displays, and a processor coupled with the first sensor, the second sensor, the first wearable display and the second wearable display. The processor is configured to obtain the first and second orientations from the first and second sensors, respectively, and to control the first wearable display to display a first image to the first crew member, and to control the second wearable display to display a second image to the second crew member, and to control the first wearable display to display the second image to the first crew member when the first orientation comprises a first predetermined orientation.

Abstract: A ceramic matrix composite (“CMC”) center body may be positioned around an austenitic nickel-chromium-based superalloy attachment ring. The attachment ring may be integrally formed with a turbine engine case. The attachment ring may have a greater coefficient of thermal expansion than the center body. A plurality of pins may be inserted through apertures in the center body and coupled to the attachment ring. The pins may slide within the apertures, allowing the attachment ring to expand without applying a load on the center body.

Abstract: Aircraft landing gear assemblies and aircraft are provided. A landing gear assembly includes a main post and a light element cluster. The main post has a non-rotating portion and a rotatable steering portion. The light element cluster is associated with the non-rotating portion and includes at least two independently illuminating sections.

Abstract: An integrated power distribution, data network, and control architecture for a vehicle is provided that includes nodes distributed throughout the vehicle. Each node includes power distribution (PD) and data collection and distribution (DCD) components. The PD components receive electrical power from a source external to the node and distribute and control the electrical power supplied to active and passive electrical loads that are external to the node. The PD components include an electrical power input interface configured to receive an electrical power input from a source external to the node, and one or more power control modules. Each power control module can control the electrical power supplied to one or more electrical power output interfaces that supply power to the active and passive electrical loads. The DCD components receive data from data sources external to the node and transmit data to data consumers external to the node.

Abstract: A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to measure the pressure field. The system further includes, but is not limited to, a controller that is communicatively coupled with the plurality of pressure sensors. The controller is configured to receive information that is indicative of the pressure field from the plurality of pressure sensors. The controller is also configured to determine when the pressure field deviates from a desired pressure field based on the information. The controller is also configured to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.

Abstract: An apparatus for controlling a hydraulically-actuated brake of an aircraft includes a brake control unit. The brake control unit is configured to receive a brake signal from an operator of the aircraft. A pump is in fluidic communication with a reservoir for holding hydraulic fluid and the brake for supplying the hydraulic fluid from the reservoir to the brake. An electric motor is in communication with the brake control unit and coupled to the pump to control pressure of the hydraulic fluid supplied by the pump in accordance with the brake signal.

Abstract: An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

Abstract: Aircraft landing gear assemblies and aircraft are provided. A landing gear assembly includes a main post and a light element cluster. The main post has a non-rotating portion and a rotatable steering portion. The light element cluster is associated with the non-rotating portion and includes at least two independently illuminating sections.

Abstract: Systems and methods are provided for monitoring, recording and/or reporting information about incidents that occur within proximity of an aircraft. When an incident monitoring mode is activated, external imagers of the aircraft begin recording of video images outside the aircraft in a temporary buffer as pre-event video data. Motion sensors that detect movement in the vicinity of the aircraft, and movement sensors that detect movement of the aircraft are also enabled. When a sensor detects a trigger event, an incident report file (IRF) is saved that includes the pre-event video data that is stored in the temporary buffer. Post-event video images are then recorded in the IRF as post-event video data until a condition occurs. Alarm signals that are perceptible outside the aircraft, and an incident report message can be generated and communicated to an external computer to indicate that an incident has occurred in proximity of the aircraft.

Abstract: An apparatus for controlling a hydraulically-actuated brake of an aircraft includes a brake control unit. The brake control unit is configured to receive a brake signal from an operator of the aircraft. A pump is in fluidic communication with a reservoir for holding hydraulic fluid and the brake for supplying the hydraulic fluid from the reservoir to the brake. An electric motor is in communication with the brake control unit and coupled to the pump to control pressure of the hydraulic fluid supplied by the pump in accordance with the brake signal.

Abstract: A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module.

Abstract: An electric supercharger comprises a motor, for example a switched reluctance motor. The motor includes a stator assembly (101) comprising a plurality of pairs of windings (103A-C), each pair of windings (103A-C) comprising a first winding for forming a first pole and a second winding for forming a second, opposite, pole, each winding having an input termination (105) and an output termination (107). The terminations (105, 107) of each pair of windings (103A-C) are arranged such that the input terminations (105) for the first and second windings are located adjacent one another and the output terminations (107) of the first and second windings are located adjacent one another.

Abstract: An apparatus for supplying an internal combustion engine with a compressed air charge is disclosed. The apparatus includes a first compressing device, for example a turbocharger, and a second compressing device, for example an electric supercharger. The second compressing device is downstream of the first compressing device. A part, for example the bearing assembly, of the second compressing device is thermally shielded from the heat of the compressed air charge by a labyrinth seal.

Abstract: A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module.

Abstract: Systems and aircraft for avoiding a collision between an obstacle an aircraft on a ground surface are provided. In some embodiments, the aircraft includes a wing and a stabilizer and a collision avoidance system includes proximity sensors, video imagers, and a display. Proximity sensors are disposed on the wing and the stabilizer. The respective proximity sensors are configured to transmit first and second obstacle detection signals. A first video imager is disposed on the wing and a second video imager is disposed on a rear portion of the aircraft. The respective video imagers are configured to generate video signals associated with the wing and with the stabilizer. The display is configured to generate video images of the regions in response to detection of objects in the regions.

Abstract: The disclosed embodiments relate to methods and systems for avoiding a collision between an obstacle and a vehicle, such as an aircraft, on a ground surface. A processor receives a detection signal from one of a plurality of proximity sensors. The detection signal indicates that the obstacle has been detected. In response to receiving the detection signal, a video image signal is transmitted from the processor to a display in the cockpit of the aircraft. The video image signal corresponds to a particular video imager that is associated with the particular proximity sensor that detected the obstacle. A video image, of a particular region around the aircraft that includes the obstacle is displayed on a display. In response to receiving the detection signal, the processor can also transmit an alert signal, and a brake activation signal to activate a braking system to prevent the aircraft from colliding with the obstacle.

Abstract: The disclosed embodiments relate to methods and systems for avoiding a collision between an aircraft and an obstacle when the aircraft is being moved on a ground surface via a ground vehicle. When a processor onboard the aircraft determines that the obstacle is located in proximity to the aircraft, the processor generates a warning generator signal, which causes an apparatus to communicate a warning signal that is perceptible to an operator of the ground vehicle to warn the operator of the obstacle.